The transition point for a flow can be found using____(a) Average of Reynolds numbers at leading and trailing edges(b) It is always the mid-chord(c) Hit and trial methods(d) Critical Reynolds numberThe question was posed to me in homework.Origin of the question is Turbulent Flow in portion Incompressible Flow over Airfoils of Aerodynamics

The transition point for a flow can be found using____(a) Average of R

1.	The transition point for a flow can be found using____(a) Average of Reynolds numbers at leading and trailing edges(b) It is always the mid-chord(c) Hit and trial methods(d) Critical Reynolds numberThe question was posed to me in homework.Origin of the question is Turbulent Flow in portion Incompressible Flow over Airfoils of Aerodynamics
Answer» The correct option is (d) Critical Reynolds number Best EXPLANATION: The critical Reynolds number is usually found from EXPERIMENTS and then using the free-stream flow parameters we can calculate the critical point, which is where the transition from laminar to TURBULENT flow takes place. All the other options are not the right ways to find the transition point.

Discussion

No Comment Found

Related InterviewSolutions

The defining assumption for finding the skin- friction drag on an airfoil is____(a) Airfoil is new low-speed airfoil(b) Skin- friction acts due to shear force(c) Airfoil has a zero angle of attack(d) Airfoil is considered a flat plate at zero angle of attackThe question was asked by my school principal while I was bunking the class.I would like to ask this question from Laminar Flow topic in portion Incompressible Flow over Airfoils of Aerodynamics
Enlist the computer methods used which benefitted the airfoil performance along with wind- tunnel testing.(a) Panel method(b) Advanced viscous flow solutions(c) Panel method and advanced viscous flow solutions(d) Hit – and – trial methodsI got this question in semester exam.My query is from Modern Low Speed Airfoils topic in chapter Incompressible Flow over Airfoils of Aerodynamics
The pressure drag in a fully attached flow over an airfoil is zero.(a) True(b) FalseI got this question by my school principal while I was bunking the class.My query is from Viscous Flow in division Incompressible Flow over Airfoils of Aerodynamics
How to increase the critical angle of attack?(a) Reduce the camber(b) Increase the camber(c) Increase the thickness(d) Reduce the thicknessThis question was posed to me in examination.This is a very interesting question from The Cambered Airfoil topic in chapter Incompressible Flow over Airfoils of Aerodynamics
The quarter-chord is the center of pressure for a cambered airfoil.(a) False(b) TrueThis question was addressed to me in an online interview.Query is from The Cambered Airfoil topic in portion Incompressible Flow over Airfoils of Aerodynamics
The camber line is not a streamline of flow for a cambered airfoil according to the thin airfoil theory.(a) Always true(b) Always false(c) True only for thin airfoils(d) Depends on the camber distributionI had been asked this question by my college professor while I was bunking the class.Query is from The Cambered Airfoil topic in chapter Incompressible Flow over Airfoils of Aerodynamics
The lift coefficient for a thin symmetrical airfoil is given by______(a) cl = πα(b) cl = π^2α(c) cl = 2πα(d) cl = πα^2I have been asked this question in an online interview.Asked question is from The Symmetric Airfoil topic in chapter Incompressible Flow over Airfoils of Aerodynamics
How the circulation around the airfoil?(a) Positive(b) Negative(c) Constant(d) Slightly variesThis question was addressed to me in an online quiz.The question is from Kelvin’s Circulation Theorem and the Starting Vortex topic in portion Incompressible Flow over Airfoils of Aerodynamics
Is circulation around the closed circuit is zero?(a) True(b) FalseI had been asked this question in a job interview.I would like to ask this question from Kelvin’s Circulation Theorem and the Starting Vortex in portion Incompressible Flow over Airfoils of Aerodynamics
Generation of lift is accompanied by a starting vortex at the trailing edge. If the flow is inviscid, this will not happen. What reason can best describe this?(a) There is no boundary layer formation, hence no vorticity(b) Kutta Condition is enforced(c) Kelvin’s Theorem is violated(d) Starting Vortex dies off instantlyI had been asked this question in my homework.My question is based upon Kelvin’s Circulation Theorem and the Starting Vortex in section Incompressible Flow over Airfoils of Aerodynamics

Discussion

No Comment Found

Related InterviewSolutions

Reply to Comment